A multi-satellite stacking system

Abstract

This disclosure relates to a multi-satellite stacking system, including a rocket adapter and multiple satellites stacked thereon and locked by a release device. The release device includes a locking part and a ejection part. The locking part includes first and second locking members movably connected and held taut by a release mechanism. The first locking member is hinged to the rocket adapter, and the top of the second locking member presses against the end face of the topmost satellite. After the release mechanism is released, the second locking member moves towards the topmost satellite via a first elastic member to unlock. The ejection part is movably connected to the rocket adapter and pre-presses the first locking member via a second elastic member. After the second locking member unlocks, the ejection part ejects the first locking member via the second elastic member. The multi-satellite stacking system of this disclosure has strong engineering implementation value. The unlocking and ejection processes of the release device are precisely coordinated, avoiding jamming during the release of multiple satellites, improving the safety of satellite release, and has advantages such as high clamping stiffness, light weight, high load-bearing capacity, and reliable separation.

Description

Technical Field

[0001] This disclosure relates to the field of spacecraft, and more specifically to a multi-satellite stacking system. Background Technology

[0002] Among existing aerospace technologies, stacked satellite launch technology has attracted much attention due to its ability to improve launch efficiency and reduce costs. However, traditional stacked satellites face numerous challenges. On the one hand, they suffer from low structural stiffness and poor bending moment resistance; for example, common stacked satellite constellations are supported only by a few connecting sleeves at the bottom, resulting in a poor mechanical environment for individual payloads. On the other hand, the connection and separation mechanisms have defects: excessive preload during connection increases structural load, and unlocking can easily cause impact. Therefore, there is an urgent need for a technical solution that can address these problems and optimize the release mechanism to improve release safety. Summary of the Invention

[0003] This disclosure provides a multi-satellite stacking system to address the problems existing in the prior art.

[0004] According to a first aspect of this disclosure, a multi-satellite stacking system is provided, including a rocket adapter and a plurality of satellites sequentially stacked on the rocket adapter, the plurality of satellites being configured to be locked together by a release device; wherein the release device includes:

[0005] The locking part is configured to include a first locking member and a second locking member that are movably connected; the first locking member and the second locking member are configured to be held in a tensioned state by a release mechanism; the first locking member is configured to be hinged to the rocket adapter, and the top end of the second locking member is configured to press against the end face of the top satellite; when the release mechanism releases the second locking member, the second locking member is configured to move towards the top satellite under the action of a first elastic member to unlock from the top satellite;

[0006] The ejector portion is configured to be movably connected to the rocket adapter and is configured to be pre-pressed onto the first locking member by a second elastic member; the ejector portion is configured to push the first locking member outward under the action of the second elastic member after the second locking member unlocks the top satellite.

[0007] In one embodiment of this disclosure, the first locking member and the second locking member are configured to engage via a guide mechanism, wherein the second locking member is configured to move along its axial direction under the guidance of the guide mechanism.

[0008] In one embodiment of this disclosure, the guiding mechanism includes a first guide seat disposed on the first locking member and a second guide seat disposed on the second locking member; a guide post is disposed on one of the first guide seat and the second guide seat, and a guide hole is disposed on the other for guiding and engaging with the guide post.

[0009] In one embodiment of this disclosure, two guide posts and two guide holes are provided, and the two guide posts and guide holes are configured to be symmetrical with respect to the axes of the first locking member and the second locking member.

[0010] In one embodiment of this disclosure, the first elastic member is configured to be sleeved on the guide post, one end of the first elastic member is configured to abut against the first guide seat, and the other end is configured to abut against the second guide seat.

[0011] In one embodiment of this disclosure, the release device is an explosive bolt, the two ends of which are configured to be connected to the first locking member and the second locking member, respectively.

[0012] In one embodiment of this disclosure, the first locking member and the second locking member are configured as rods, and the explosive bolt, the first locking member, and the second locking member are configured to be coaxially arranged.

[0013] In one embodiment of this disclosure, a locking seat is provided on the top satellite, and a pressing part is provided at the top of the second locking member, the pressing part being configured to press against the top end face of the locking seat.

[0014] In one embodiment of this disclosure, the top of the second locking member is provided with a threaded section, and the pressing part is configured to be sleeved on the threaded section; a first locking nut is provided on the threaded section at a position outside the pressing part, and the first locking nut is configured to press the pressing part against the end face of the locking seat by rotation.

[0015] In one embodiment of this disclosure, a second locking nut is provided on the threaded segment at the bottom of the clamping part, the second locking nut being configured to abut against the clamping part by rotation.

[0016] In one embodiment of this disclosure, a plurality of release devices are provided, and the plurality of release devices are configured to be distributed in the circumferential direction of the satellite.

[0017] In one embodiment of this disclosure, the satellite is generally cross-shaped, and the four side walls of the satellite are provided with protrusions extending in their respective directions. The connection position of two adjacent protrusions is constructed to have a chamfered structure. The locking seat is constructed to be disposed on the chamfered structure of the top-level satellite.

[0018] In one embodiment of this disclosure, the rocket adapter is provided with a mounting base, and the first locking member is configured to be hinged to the mounting base via a rotating part; the rotating part is provided with a locking hole; the mounting base is provided with a locking pin, and the locking pin is configured to be pre-pressed on the end face of the rotating part by a third elastic member; the rotating part is configured to be rotated relative to the mounting base to a predetermined angle, and the locking pin is configured to extend into the locking hole under the action of the third elastic member to lock the rotating part.

[0019] In one embodiment of this disclosure, a positioning unit is provided between the upper satellite and the lower satellite; the positioning unit is a first truncated cone and a second truncated cone respectively provided at the bottom of the upper satellite and the top of the lower satellite.

[0020] In one embodiment of this disclosure, the conical surfaces of the first frustum and the second frustum have a predetermined angle.

[0021] One beneficial effect of this disclosure is that the release device can pre-tighten and release multiple satellites stacked on the rocket adapter. The linkage between its locking part and the ejection part can effectively avoid the jamming problem in the release of multi-layer satellites, improve the safety of satellite release, and has the advantages of high clamping stiffness, light weight, high load-bearing capacity, and reliable separation. At the same time, compared with traditional stacked satellites, the overall configuration of the release device disclosed in this disclosure has no complex central load-bearing cylinder, which can effectively reduce weight and volume occupation, increase the proportion of the overall satellite weight, adapt to the needs of batch launch and rapid networking, and take into account both reliability and economy.

[0022] Other features and advantages of this disclosure will become clear from the following detailed description of exemplary embodiments with reference to the accompanying drawings. Attached Figure Description

[0023] The accompanying drawings, which are incorporated in and form a part of this specification, illustrate embodiments of the present disclosure and, together with their description, serve to explain the principles of the present disclosure.

[0024] Figure 1 This is a schematic diagram of the overall structure of the multi-satellite stacking system disclosed herein;

[0025] Figure 2 yes Figure 1 Enlarged view of point A in the middle;

[0026] Figure 3 yes Figure 1 Enlarged view of point B in the middle;

[0027] Figure 4 yes Figure 1 Enlarged view of point C in the middle;

[0028] Figure 5This is a cross-sectional view of the ejector portion in an embodiment of this disclosure;

[0029] Figure 6 This is a top view of the disclosed multi-satellite stacking system;

[0030] Figure 7 This is a schematic diagram of the upper surface of the satellite in an embodiment of this disclosure;

[0031] Figure 8 yes Figure 7 Enlarged view at point D;

[0032] Figure 9 This is a schematic diagram of the mating structure of the cones between two adjacent satellite layers.

[0033] Figures 1 to 9 The one-to-one correspondence between the component names and the reference numerals in the figures is as follows:

[0034] 10. Rocket adapter; 20. Satellite; 21. Protrusion; 22. Chamfered structure; 31. First locking element; 311. Rotating part; 32. Second locking element; 321. Threaded section; 41. First elastic element; 42. Second elastic element; 50. Ejection part; 61. First guide seat; 62. Second guide seat; 63. Guide post; 64. Explosion bolt; 71. Locking seat; 72. Clamping part; 73. First locking nut; 74. Second locking nut; 80. Mounting seat; 81. Locking pin; 91. First cone; 92. Second cone. Detailed Implementation

[0035] Various exemplary embodiments of the present disclosure will now be described in detail with reference to the accompanying drawings. It should be noted that, unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps set forth in these embodiments do not limit the scope of the present disclosure.

[0036] The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit this disclosure or its application or use.

[0037] Techniques, methods, and equipment known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and equipment should be considered part of the specification.

[0038] It should be noted that similar labels and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be discussed further in subsequent figures.

[0039] In this article, terms such as "up," "down," "front," "back," "left," and "right" are used only to indicate the relative positional relationship between related parts, rather than to define the absolute position of these related parts.

[0040] In this article, "first," "second," etc., are used only to distinguish one another, and not to indicate degree of importance, order, or prerequisite for each other.

[0041] In this document, terms such as “equal” and “same” are not strict mathematical and / or geometric limitations, but also include errors that are understandable to those skilled in the art and permissible in manufacturing or use.

[0042] This disclosure provides a multi-satellite stacking system, including a rocket adapter and multiple satellites stacked thereon and locked by a release device. The release device includes a locking part and an ejection part. The locking part includes a first and a second locking member movably connected, which are held taut by a release mechanism. The first locking member is hinged to the rocket adapter, and the top of the second locking member presses against the end face of the top satellite. After the release mechanism is released, the second locking member moves towards the top satellite via a first elastic member to unlock. The ejection part is movably connected to the rocket adapter and pre-presses the first locking member via a second elastic member. When the second locking member unlocks, the ejection part ejects the first locking member via the second elastic member. The multi-satellite stacking system of this disclosure has strong engineering implementation value. The unlocking and ejection processes of the release device are precisely coordinated, avoiding jamming during the release of multiple satellites, improving the safety of satellite release, and has advantages such as high clamping stiffness, light weight, high load-bearing capacity, and reliable separation.

[0043] The specific embodiments of this disclosure are described below with reference to the accompanying drawings.

[0044] refer to Figures 1 to 5 This disclosure provides a multi-satellite stacking system, including a rocket adapter 10 and a plurality of satellites 20 stacked sequentially on the rocket adapter 10, the plurality of satellites 20 being locked together by a release device.

[0045] Specifically, multiple satellites 20 are stacked on the rocket adapter 10 in a top-to-bottom manner. Each satellite 20 adopts a flat panel configuration with a low layer height to reduce the overall height of the stacked satellites. The layer height of each satellite 20 is sufficient to provide space for ground payloads while preventing collisions between satellites 20 during separation.

[0046] In one embodiment of this disclosure, when multiple satellites 20 are stacked, the side of each satellite 20 closest to its center of mass (either the bottom or top surface) faces downwards, while the other side faces upwards. This ensures that the overall center of gravity of the stack is downwards, i.e., towards the rocket adapter 10. Furthermore, a downward-facing center of mass facilitates a smoother release, avoiding the tumbling problems and collisions caused by an upward-facing center of mass. Multiple satellites 20 are pressed together and locked together by a release device using a top-to-bottom clamping method. The rocket adapter 10 carries the multi-layered stacked satellites 20 into a predetermined orbit. After the launch vehicle completes the pitch angular velocity setting, it receives a satellite-rocket separation signal, triggering the satellite 20 separation action.

[0047] The release device includes a locking part and an ejection part 50. The locking part includes a first locking member 31 and a second locking member 32 that are movably connected. The first locking member 31 and the second locking member 32 are held in a taut state by a release mechanism. The first locking member 31 is hinged to the rocket adapter 10, and the top end of the second locking member 32 presses against the end face of the topmost satellite 20, thereby pressing the stacked satellites 20 onto the rocket adapter 10 by the first locking member 31 and the second locking member 32. That is, the satellites below the topmost satellite are not fixed by any restraint device, but only by the second locking member 32 pressing against the end face of the topmost satellite, thereby securing all the satellites to the rocket adapter 10.

[0048] like Figure 1 As shown, the first locking member 31 and the second locking member 32 are coaxially arranged and connected together by a release device. The first locking member 31, the second locking member 32, and the release device work together to fix the rocket adapter 10 and the multi-layer satellite 20 together and keep them in a compressed state. The materials selected for the first locking member 31 and the second locking member 32 need to meet the load-bearing requirements of tens of tons of pre-tightening force. Solid aluminum alloy structures are preferred, taking into account both lightweight and high strength characteristics.

[0049] After the release mechanism releases the second locking member 32, the second locking member 32 moves towards the top-level satellite 20 under the action of the first elastic member 41 to unlock it. Figure 3As shown, when the release device releases the second locking member 32, the original clamping state is released, the clamping force applied to the first elastic member 41 disappears, and the thrust generated by the rebound of the first elastic member 41 pushes the second locking member 32 towards the direction of the top satellite 20. Originally, the top of the second locking member 32 was pressed against the end face of the top satellite 20. Under the thrust of the first elastic member 41, the second locking member 32 is released from the lock state with the top satellite 20. As a result, the stacked satellites 20 as a whole lose the clamping force. At the initial separation angle, the satellites 20, under the influence of the orbital environment and their own attitude control, gradually increase the distance from the adjacent satellites 20. Moreover, because the single satellite 20 adopts a flat plate configuration and has a low layer height, the risk of collision between satellites 20 during the separation process is effectively avoided.

[0050] The ejector portion 50 is movably connected to the rocket adapter 10 and is pre-pressed onto the first locking member 31 by the second elastic member 42. For example... Figure 2 As shown, the ejector part 50 is located between the rocket adapter 10 and the first locking member 31. One end of the ejector part 50 is movably connected to the rocket adapter 10, and the other end abuts against the first locking member 31.

[0051] Specifically, such as Figure 5 As shown, the ejector portion 50 is configured to be pre-pressed onto the first locking member 31 by a second elastic member 42. The second elastic member 42 may be a compression spring sleeved on the ejector portion 50, providing a clamping force to the ejector portion 50. In another embodiment of this disclosure, the ejector portion 50 includes a base with an inner cavity and an ejector sleeve movably connected within the base, with the second elastic member 42 housed within the cavities of the base and the ejector sleeve. In this disclosure, the second elastic member 42 is preferably a compression spring; under the action of the second elastic member 42, one end of the ejector sleeve abuts against the first locking member 31. The ejector portion 50 utilizes the elastic deformation and recovery characteristics of the second elastic member 42 to control the force transmission of the second elastic member 42 onto the ejector sleeve through the locked or unlocked state of the first locking member 31, thereby realizing the ejection function of the ejector portion 50.

[0052] The ejector 50 is configured such that when the second locking member 32 unlocks the top satellite 20, the first locking member 31 is ejected outward under the action of the second elastic member 42.

[0053] Specifically, when the first locking member 31 and the second locking member 32 are in a restrained state, the second locking member 32 is pressed against the end face of the top satellite 20, which provides a restraining force in the stacking direction for all satellites 20. At this time, the ejector 50, which is pre-pressed on the first locking member 31, cannot push the first locking member 31 to move. When the release device releases the second locking member 32, the original pressing state is released. At this time, not only does the second locking member 32 move towards the top satellite to unlock all satellites, but the restraining force of the first locking member 31 in the stacking direction also disappears. At this time, the ejector 50 pushes the first locking member 31 outward under the thrust of the second elastic member 42. The first locking member 31, along with the second locking member 32, moves synchronously towards the outside of the stacked satellites to clear the release path of the satellites 20. After all satellites 20 are freed from the restraint of the locking member, they detach from the rocket adapter 10 and are freely released into space.

[0054] In order to ensure that the ejector portion 50 has a large pushing displacement on the first locking member 31, in one embodiment of this disclosure, the ejector portion 50 is provided at a position adjacent to the hinge of the first locking member 31, thereby maximizing the distance that the first locking member 31 is pushed outward.

[0055] In one embodiment of this disclosure, the first locking member 31 and the second locking member 32 are guided and engaged by a guiding mechanism, and the second locking member 32 can move along its axial direction under the guidance of the guiding mechanism. Specifically, as shown... Figure 1 As shown, the first locking member 31 and the second locking member 32 are independent components. After the release device releases the second locking member 32, the second locking member 32 needs to move towards the top-level satellite 20. During this period, the direction of movement of the second locking member 32 must not deviate, otherwise it will lead to failure to unlock with the top-level satellite 20, resulting in the satellite 20 being unable to separate freely and also posing a risk of collision. Therefore, the second locking member 32 needs to maintain its axial movement towards the top-level satellite 20 under the guidance of the guiding mechanism.

[0056] In one embodiment of this disclosure, reference is made to Figure 3 The guiding mechanism includes a first guide seat 61 disposed on the first locking member 31, and a second guide seat 62 disposed on the second locking member 32. (See reference) Figure 1 and Figure 3 One end of the first locking member 31 is hinged to the rocket adapter 10, and the other end is connected to the first guide seat 61; one end of the second locking member 32 is locked to the top-level satellite 20, and the other end is connected to the second guide seat 62. The first locking member 31 and the first guide seat 61 can be connected by a threaded connection or by welding; the specific connection method is not limited in this disclosure. The connection method between the second locking member 32 and the second guide seat 62 is similar.

[0057] In one specific embodiment of this disclosure, the first locking member 31 is provided with a first threaded hole at one end connected to the first guide seat 61, and the first guide seat 61 is provided with a first threaded rod that can cooperate with the first threaded hole at one end connected to the first locking member 31. During installation, the first threaded rod of the first guide seat 61 is fully screwed into the first threaded hole, and the thread structure of the first threaded rod cooperates with the thread structure of the first threaded hole, so that the first guide seat 61 is installed on the first locking member 31.

[0058] Similarly, the second locking member 32 and the second guide member are also connected by a threaded connection. Specifically, the end of the second locking member 32 connected to the second guide seat 62 is provided with a second threaded hole, and the end of the second guide seat 62 connected to the second locking member 32 is provided with a second threaded rod that can mate with the second threaded hole; during installation, the second threaded rod of the second guide seat 62 is fully screwed into the second threaded hole, so that the second guide seat 62 is installed on the second locking member 32.

[0059] A guide post 63 is provided on one of the first guide seat 61 and the second guide seat 62, and a guide hole is provided on the other to guide and cooperate with the guide post 63.

[0060] In one specific embodiment of this disclosure, reference continues to be made. Figure 3 A guide post 63 is provided on the second guide seat 62, extending from the base end face of the second guide seat 62 along its axial direction; a guide hole is provided on the first guide seat 61 to guide and engage with the guide post 63. When the release device releases the second locking member 32, the second locking member 32 drives the connected second guide seat 62 to move together towards the top satellite 20. At the same time, the guide post 63 engages with the guide hole to ensure that the second locking member 32 moves in the predetermined direction without deviation.

[0061] Similarly, a guide post 63 can be provided on the first guide seat 61, and a guide hole that cooperates with the guide post 63 can be provided on the second guide seat 62, which also satisfies the above-mentioned limiting conditions, and will not be elaborated on here.

[0062] In addition, the guiding mechanism can be configured in other forms, including but not limited to a guide sleeve on the guide seat and a guide post 63 that can extend into the guide sleeve. A guide sleeve is provided on one of the first guide seat 61 and the second guide seat 62, and a guide post 63 that extends into the guide sleeve and guides it is provided on the other.

[0063] In one specific embodiment of this disclosure, the guide sleeve can be configured as a hollow structure with both ends open, and its inner wall must ensure high straightness and smoothness to reduce frictional resistance during mating. The guide post 63 can be a solid cylindrical structure, and its outer diameter and the inner diameter of the guide sleeve must meet the clearance fit requirements to ensure that the column of the guide post 63 can slide smoothly in the guide sleeve, and the axes of both must be consistent with the axis of the second locking member 32 and its preset movement direction.

[0064] In one specific embodiment of this disclosure, a guide sleeve is provided on the first guide seat 61. The guide sleeve is vertically fixed to the end face of the first guide seat 61 facing the second guide seat 62, and the length of the sleeve is not less than the maximum stroke of the second locking member 32. On the second guide seat 62, a guide post 63 matching the guide sleeve is provided. One end of the guide post 63 is fixedly connected to the second guide seat 62 or can be integrally molded. The other end is partially inserted into the guide sleeve when the first and second locking members 32 are in the initial locked state, forming the initial guiding positioning.

[0065] When the release device releases the second locking member 32, the second locking member 32 drives the second guide seat 62 to move towards the top satellite 20. At this time, the guide post 63 slides synchronously along the inner wall of the guide sleeve. The inner wall of the guide sleeve restricts the radial displacement of the guide post 63, preventing the second locking member 32 from shifting left or right or rotating. At the same time, the cooperation between the guide sleeve and the guide post 63 can compensate for minor deviations in the movement of the second locking member 32, ensuring that it always moves along a preset straight trajectory.

[0066] Similarly, a guide sleeve can be set on the second guide seat 62 and a guide post 63 that cooperates with it can be set on the first guide seat 61. As long as the dimensions of the guide sleeve and the guide post 63 are compatible and their axes are consistent with the movement direction of the second locking member 32, the same guiding effect can be achieved. This will not be elaborated on further here.

[0067] In one specific embodiment of this disclosure, two guide posts 63 and two guide holes are provided, and the two guide posts 63 and guide holes are symmetrical with respect to the axes of the first locking member 31 and the second locking member 32.

[0068] Specifically, two guide holes penetrating the base are symmetrically arranged on both sides of the first guide seat 61 along its axis; two guide posts 63 are symmetrically arranged on both sides of the second guide seat 62 along its axis. The two guide posts 63 extend from the base of the second guide seat 62 along the axial direction and are threaded at their ends. The two guide holes on the first guide seat 61 can correspond to and engage with the two guide posts 63 on the second guide seat 62, meaning the two guide posts 63 on the second guide seat 62 can pass through the two guide holes on the first guide seat 61. Furthermore, a limiting nut that engages with the thread is screwed into its end.

[0069] Furthermore, the two guide posts 63 on the second guide seat 62 are identical in shape and size. The cross-section of the guide post 63 can be a regular polygon, a circle, or another shape. Simultaneously, the shapes of the two guide holes on the first guide seat 61 must be compatible with the two guide posts 63 on the second guide seat 62. For example, if the cross-section of the two guide posts 63 on the second guide seat 62 is circular, then the shapes of the two guide holes on the first guide seat 61 that mate with them should also be circular, and the diameter of the guide post 63 must be slightly smaller than the diameter of the guide hole, so that the displacement of the guide post 63 relative to the guide hole is not affected by friction. Similarly, if the cross-section of the two guide holes on the second guide seat 62 is a regular polygon, then the shapes of the two guide holes on the first guide seat 61 must also ensure that the displacement of the guide post 63 relative to the guide hole is not affected by friction. This will not be elaborated further here.

[0070] After the two guide pins 63 on the second guide seat 62 pass through the two guide holes on the first guide seat 61, a limiting nut that engages with the thread is screwed into their ends. The limiting nut ensures that the guide pin 63 will not come out of the guide hole after frictionless sliding relative to the guide hole. Specifically, when the second locking member 32 is unlocked from the top satellite 20, the release device releases the second locking member 32, causing the second locking member 32 to move towards the top satellite 20; the second locking member 32 also drives the connected second guide seat 62 to move towards the top satellite 20. Therefore, a limiting nut needs to be set at the end of the guide pin 63 to prevent the guide pin 63 from coming out of the guide hole. This ensures that even if the second locking member 32 moves towards the top satellite 20 after unlocking, it can still be connected to the first locking member 31 through the guiding mechanism.

[0071] The coaxiality of the movement of the second locking member 32 and the first locking member 31 can be maintained by the cooperation of the two guide posts 63 and the guide holes. Similarly, when the guide posts 63 are located in the first guide seat 61 and the guide holes are located in the second guide seat 62, the above conditions are also met; if the guiding mechanism adopts other forms, the coaxiality of the movement of the first locking member 31 and the second locking member 32 should also be met, which will not be elaborated on here.

[0072] In one embodiment of this disclosure, a first elastic member 41 is sleeved on a guide post 63, with one end of the first elastic member 41 abutting against a first guide seat 61 and the other end abutting against a second guide seat 62. Specifically, as shown... Figure 3 As shown, when the release device does not release the second locking member 32, the first elastic member 41 is in a compressed state, storing elastic potential energy. When the release device releases the second locking member 32, the compression constraint is released, and the elastic potential energy of the first elastic member 41 is released. It uses its own elastic force to provide power for the second locking member 32 to drive the second guide seat 62 to move towards the top satellite 20. At the same time, it uses its own elasticity to buffer the impact force of the release device, avoiding the application of impact force beyond its bearing capacity to the first guide seat 61 and the first locking member 31, which could cause structural deformation or reverse displacement.

[0073] The first elastic element 41 can take the form of a compression spring or other component with elastic recovery capability. In this embodiment, a compression spring is preferred. Its wire diameter and number of coils need to be calculated and determined according to the preload release requirements to ensure that the elastic force can effectively push the second locking element 32 to complete the unlocking action, while also buffering the impact force during release. Throughout this process, the connection between the first guide seat 61 and the second guide seat 62 via the first elastic element 41 and the guide structure is maintained to ensure the stable operation of the guide mechanism.

[0074] In one embodiment of this disclosure, the release device is an explosive bolt 64, with a first locking member 31 and a second locking member 32 connected to its two ends, respectively. Specifically, the explosive bolt 64 is a high-strength bolt, with a pyrotechnic device and a debris containment system in its middle portion to ensure that all debris generated by the explosion of the pyrotechnic device is contained within the explosive bolt 64 and will not scatter out as "space debris" or "shrapnel" that could harm the spacecraft. The explosive bolt 64 can be of common shearing, fracture, or unlocking types, and its specific type is not limited in this disclosure.

[0075] In one specific embodiment of this disclosure, the two ends of the explosive bolt 64 can be connected to a first locking member 31 and a second locking member 32, respectively. The end of the first locking member 31 connected to the explosive bolt 64 has a threaded hole that can engage with the thread at one end of the explosive bolt 64. Similarly, the second locking member 32 also has a threaded hole that can engage with the thread at the other end of the explosive bolt 64. The explosive bolt 64 keeps the first locking member 31 and the second locking member 32 in a taut state, ensuring that the multi-layer satellite 20 is stably locked during the launch phase. When the pyrotechnic device inside the explosive bolt 64 detonates, the explosive bolt 64 breaks under the detonation force, releasing the taut constraint on the first locking member 31 and the second locking member 32. At this time, the first elastic member 41, which was originally in a compressed state, synchronously recovers from the compressed state to a free state, generating a rebound force along its axial direction. This thrust pushes the second locking member 32 toward the top-layer satellite 20 to unlock it.

[0076] In one embodiment of this disclosure, the first locking member 31 and the second locking member 32 are constructed in the shape of rods, and the explosion bolt 64, the first locking member 31, and the second locking member 32 are coaxially arranged. Specifically, the first locking member 31 and the second locking member 32 are solid aluminum alloy structures, capable of withstanding tens of tons of preload force, meeting the strength requirements for preload of multi-layer stacked satellites 20 in the space environment. Key dimensions such as the rod diameter and wall thickness need to be determined through strength verification to ensure that no plastic deformation or fracture occurs under preload conditions. Specific processing details not mentioned are not limited in this disclosure. The coaxial arrangement of the explosion bolt 64, the first locking member 31, and the second locking member 32 ensures that the preload force is uniformly transmitted along the axial direction, avoiding local stress concentration due to force eccentricity.

[0077] In one specific embodiment of this disclosure, the explosive bolt 64, acting as a release device, is disposed between the first guide seat 61 and the second guide seat 62 of the guide mechanism, and is located at the exact center of the two symmetrically distributed guide posts 63. The first locking member 31 and the second locking member 32 together form a solid rod-shaped structure, the axis of which coincides with the axis of the explosive bolt 64, ensuring that the preload is uniformly transmitted axially to the locking part and the guide mechanism, avoiding local stress concentration due to force eccentricity. At the same time, this coaxial arrangement can reduce the matching deviation of the guide mechanism, ensure the accuracy of the movement trajectory of the second locking member 32 when unlocking, and further improve the reliability of the unlocking action.

[0078] Specifically, the first guide seat 61 has a first clearance channel penetrating its body at its middle position, and the end of the first locking member 31 connected to the first guide seat 61 has a first threaded hole, which is coaxial with the first clearance channel of the first guide seat 61. Correspondingly, the second guide seat 62 has a second clearance channel penetrating its body at its middle position, and the end of the second locking member 32 connected to the second guide seat 62 has a second threaded hole, which is also coaxial with the second clearance channel of the second guide seat 62.

[0079] The explosive bolt 64, through its external threads at both ends, passes through the first clearance channel and then connects to the first internal threaded hole of the first locking member 31. It also passes through the second clearance channel and then connects to the second internal threaded hole of the second locking member 32, forming a threaded engagement. It does not directly connect to the channels of the first guide seat 61 or the second guide seat 62. The first clearance channel of the first guide seat 61 and the second clearance channel of the second guide seat 62 are only used to provide clearance space for the shank of the explosive bolt 64, avoiding structural interference with the guide seats.

[0080] In one specific embodiment of this disclosure, a first threaded portion penetrating the first guide seat 61 is provided at the middle position, and a second threaded portion penetrating the body of the second guide seat 62 is also provided at the middle position; a first threaded hole is provided at the end of the first locking member 31 near the first guide seat 61, and a second threaded hole is provided at the end of the second locking member 32 near the second guide seat 62.

[0081] During installation, one end of the explosion bolt 64 is screwed into and passes through the first threaded part through the threaded engagement, and protrudes from the first threaded part; the protruding part is then screwed into the first threaded hole of the first locking member 31, and then the explosion bolt 64 is tightened to the pre-tightened position using a tool; at this time, the first locking member 31 and the first guide seat 61 are connected together by the explosion bolt 64.

[0082] Similarly, the other end of the explosive bolt 64 is screwed into and through the second threaded part through the threaded engagement, and protrudes from the second threaded part; the protruding part is then screwed into the first threaded hole of the first locking member 31, and then the explosive bolt 64 is tightened to the pre-tightened position using a tool; at this time, the second locking member 32 and the second guide seat 62 are also connected together through the explosive bolt 64.

[0083] At this point, the two ends of the explosive bolt 64 are respectively connected to the first locking member 31 and the second locking member 32, and the explosive bolt 64, the first locking member 31, and the second locking member 32 are coaxially arranged, maintaining the overall tension of the release device. Upon receiving the satellite-rocket separation signal, the pyrotechnic device located inside the explosive bolt 64 ignites and detonates, causing the explosive bolt 64 to break and releasing the tension constraint on the first locking member 31 and the second locking member 32. At this time, the first elastic member 41, which was originally located on both sides of the explosive bolt 64 and was in a compressed state, synchronously returns from the compressed state to a free state, generating an upward rebound force along its axial direction; this rebound force pushes the second locking member 32 to move towards the top-level satellite 20, releasing the overall preload to unlock it from the top-level satellite 20.

[0084] In one embodiment of this disclosure, a locking seat 71 is provided on the top satellite 20, and a pressing part 72 is provided at the top end of the second locking member 32, pressing the pressing part 72 against the top end face of the locking seat 71. Specifically, as shown... Figure 4 As shown, the connection methods between the locking seat 71 and the top satellite 20 include, but are not limited to, welding and bolting. The material of the locking seat 71 must be compatible with the main body of the satellite 20 to ensure sufficient connection strength.

[0085] The clamping part 72 is disposed on the top of the second locking member 32. Its overall shape is adapted to fit and conform to the top end face of the locking seat 71, and it can be stably pressed against the top of the locking seat 71. The clamping part 72 presses against the top end face of the locking seat 71 in a surface contact manner. The two cooperate to apply the preload force transmitted from the second locking member 32 to the locking seat 71, thereby stably locking the satellite 20 in the stacking system and ensuring the stability of the satellite 20's position during the launch and orbital operation phases.

[0086] In one embodiment of this disclosure, the top of the second locking member 32 is provided with a threaded section 321, and the pressing part 72 is sleeved on the threaded section 321; a first locking nut 73 is provided on the threaded section 321 at a position outside the pressing part 72, and the first locking nut 73 presses the pressing part 72 against the end face of the locking seat 71 by rotating.

[0087] Specifically, such as Figure 4 As shown, the clamping part 72 has a block-shaped structure, which can fit and adhere to the top end face of the locking seat 71 and be stably pressed against the top of the locking seat 71. The clamping part 72 has a through hole in the middle for the threaded section 321 to pass through. The first locking nut 73 can engage with the thread of the threaded section 321, and the engagement accuracy must meet the tolerance requirements to ensure that there is no jamming during tightening, and that it can provide stable axial pressure after tightening, so that the clamping part 72 and the locking seat 71 fit tightly together.

[0088] When installing the release device of the multi-satellite 20 stacking system disclosed herein, a threaded section 321 is integrally machined on the top of the second locking member 32. After the threaded section 321 of the second locking member 32 passes through the notch provided on the locking seat 71, the first locking nut 73 is screwed into the top of the threaded section 321. The first locking nut 73 is tightened to generate downward pressure, pressing the clamping part 72 against the end face of the top of the locking seat 71, so as to realize the locking constraint of the second locking member 32 on the top satellite 20.

[0089] In one embodiment of this disclosure, a second locking nut 74 is provided on the threaded section 321 at the bottom of the clamping part 72, and the second locking nut 74 abuts against the clamping part 72 by rotation. Specifically, as Figure 4 As shown, the second locking nut 74 prevents the clamping part 72 from falling downwards due to the loss of upward constraint when the explosive bolt 64 detonates and releases the second locking member 32, thus avoiding secondary contact between the clamping part 72 and the locking seat 71 and affecting the timeliness and reliability of the unlocking action. At the same time, the second locking nut 74 can also serve as a positioning reference for the clamping part 72, making it easy to quickly adjust the position of the clamping part 72 during installation and improving assembly efficiency.

[0090] In one embodiment of this disclosure, such as Figure 1 As shown, multiple release devices are provided, distributed along the circumference of satellite 20. The even distribution of these devices along the circumference ensures a uniform distribution of the preload force on satellite 20, preventing tilting or deformation due to uneven stress. Furthermore, the redundancy of the multiple release devices enhances system reliability; even if a single release device fails, the remaining devices can maintain basic locking functionality, reducing launch risk.

[0091] In one embodiment of this disclosure, such as Figure 6 As shown, the satellite 20 is cross-shaped, and the four side walls of the satellite 20 are provided with protrusions 21 extending in their respective directions. The connection position of two adjacent protrusions 21 is constructed with a chamfered structure 22. The locking seat 71 is provided on the chamfered structure 22 of the top satellite 20.

[0092] Specifically, the cruciform satellite 20 configuration optimizes payload layout, and the protrusion 21 can be used to install external equipment such as antennas and sensors. The chamfered structure 22 design avoids stress concentration and improves the structural strength of the satellite 20. At the same time, after the chamfered structures 22 of the multi-layer satellites 20 are stacked, a space suitable for the installation of the release device is formed; this not only does not encroach on the space of the satellite 20 body, but also allows the release device to be positioned closer to the center of mass of the satellite 20, reducing the additional torque generated by the preload of the release device and further improving the stability of the stacking system. Moreover, the locking seat 71 provided on the chamfered structure 22 of the top-layer satellite 20 provides a locking point for the release device of this disclosure, so that the stacked multi-layer satellites 20 are locked to the rocket adapter 10 by the release device.

[0093] In one embodiment of this disclosure, the rocket adapter 10 is provided with a mounting base 80, and a first locking member 31 is hinged to the mounting base 80 via a rotating part 311. The rotating part 311 is provided with a locking hole, and the mounting base 80 is provided with a locking pin 81. The locking pin 81 is pre-pressed onto the end face of the rotating part 311 by a third elastic member. After the rotating part 311 rotates relative to the mounting base 80 to a predetermined angle, the locking pin 81 extends into the locking hole under the action of the third elastic member to lock the rotating part 311.

[0094] Specifically, the mounting base 80 on the rocket adapter 10 provides a mechanical interface for the installation of the locking part, and a micro switch or similar device can be installed on it to provide telemetry signals. One end of the first locking member 31 is rod-shaped and connected to the second locking member 32, while the other end has a rotating part 311 that can be adapted to and hinged with the mounting base 80, and can rotate around the bearing of the mounting base 80. In the tensioned state, the locking pin 81 on the mounting base 80 is pressed against the end face of the rotating part 311, and the locking hole located on the end face of the rotating part 311 is in a position away from the locking pin 81.

[0095] When the first locking member 31 rotates around the rotating part 311 relative to the mounting base 80 to a predetermined angle under the thrust of the ejector part 50, the locking pin 81 on the mounting base 80 automatically extends into the locking hole of the rotating part 311 under the elastic force of the third elastic member, locking the position of the first locking member 31. This locking action can prevent the first locking member 31 from swinging back during the subsequent separation of the satellite 20, avoiding collision with the satellite 20 or the rocket adapter 10, while ensuring that the first locking member 31 will not pose a risk of space debris to the orbital environment.

[0096] In one embodiment of this disclosure, a positioning unit is provided between the upper satellite and the lower satellite. The positioning unit is a first cone 91 and a second cone 92 respectively provided at the bottom of the upper satellite and the top of the lower satellite.

[0097] Specifically, to effectively prevent sideslip during the stacking of satellites 20, reference Figure 7 and Figure 8 A first truncated cone 91 is provided at the bottom of the upper satellite, and the first truncated cone 91 is configured to protrude from the bottom of the upper satellite. In a specific embodiment of this disclosure, the first truncated cone 91 is configured to form a closed or open ring structure at the bottom of the upper satellite. Similarly, a second truncated cone 92 is provided at the top of the lower satellite, and the shape of the second truncated cone 92 may be similar to the shape of the first truncated cone 91. When the two satellites are stacked together, refer to... Figure 9 The bottom end face of the upper satellite can abut against the top end face of the lower satellite, and the conical surface of the first truncated cone 91 can cooperate with the conical surface of the second truncated cone 92. Together, they constitute a two-way cooperation mechanism between the upper and lower satellites. When the satellite assembly lies on its side and is subjected to lateral shear force, no lateral relative sliding will occur between the satellites, ensuring the lateral stiffness of the satellite assembly.

[0098] From the perspective of positioning function, the precise cooperation between the first cone 91 and the second cone 92 can directly realize the rapid alignment of the upper and lower layers of satellites, and can strictly ensure the coaxiality of the satellite 20 in the stacked state, thus avoiding the problem of difficulty in installing the release device due to the offset of the satellite 20.

[0099] From the perspective of optimizing mechanical performance, this positioning unit also plays an important role in load transfer. During the rocket launch phase, it can bear part of the lateral load, significantly reducing the stress on the release device, and thus significantly improving the overall vibration and impact resistance of the satellite assembly.

[0100] Furthermore, this structural design offers two additional advantages: firstly, it simultaneously ensures the overall installation and manufacturing accuracy of Satellite 20, simplifying the assembly process and avoiding the complex procedures of traditional assembly methods; secondly, it provides reliable lateral positioning for Satellite 20, completely eliminating the risk of lateral slippage. As the main force transmission channel from top to bottom for the entire satellite, the design of this positioning unit directly determines the structural stiffness and strength performance of the satellite assembly, making it a core component ensuring the stacking stability of Satellite 20.

[0101] In one embodiment of this disclosure, the conical surfaces of the first frustum 91 and the second frustum 92 have a predetermined angle. (See reference...) Figure 9 The conical surfaces of the first truncated cone 91 and the second truncated cone 92 are not completely parallel; they have a predetermined angle. This prevents the conical surfaces of the first truncated cone 91 and the second truncated cone 92 from completely fitting together, and the distance between them is designed to gradually increase from bottom to top. This ensures that the first truncated cone 91 and the second truncated cone 92 can smoothly separate when the satellite 20 separates, avoiding the risk of separation jamming.

[0102] In one specific embodiment of this disclosure, the assembly of the multi-satellite stacking system of this disclosure is completed, and a preload force to ensure the rigidity of the satellite 20 is applied. After the rocket adapter 10 carries the multi-layer stacked satellite 20 into orbit, the pitch angular velocity is set, and a satellite-rocket separation signal is sent to it. The pyrotechnic device inside the explosive bolt 64 detonates, and the explosive bolt 64 breaks under the action of the detonation force, releasing the tension constraint on the first locking member 31 and the second locking member 32. The first elastic member 41, which was originally located on both sides of the explosive bolt 64 and was in a compressed state, simultaneously recovers from the compressed state to a free state, generating a rebound force along its axial direction. This thrust pushes the second locking member 32 to move towards the top-level satellite 20 under the guidance of the guiding mechanism, so as to unlock it from the top-level satellite 20. At this point, the original clamping state is released. Under the push of the second elastic member 42, the ejector part 50 pushes the first locking member 31 to swing outward. The first locking member 31 drives the second locking member 32 through the guide mechanism. When the first locking member 31 rotates around the rotating part 311 relative to the mounting base 80 to a predetermined angle, the locking pin 81 on the mounting base 80 automatically extends into the locking hole of the rotating part 311 under the elastic force of the third elastic member, locking the position of the first locking member 31 to clear the release path of the satellite 20. After all the satellites 20 are freed from the restraint of the locking part, they disengage from the rocket adapter 10, and the satellites 20 gradually pull apart at the initial angle to complete the separation.

[0103] The various embodiments of this disclosure have been described above. These descriptions are exemplary and not exhaustive, and are not limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments. The terminology used herein is chosen to best explain the principles, practical application, or technical improvements to the embodiments in the market, or to enable others skilled in the art to understand the embodiments disclosed herein. The scope of this disclosure is defined by the appended claims.

Claims

1. A multi-satellite stacking system, characterized in that, The system includes a rocket adapter (10) and a plurality of satellites (20) stacked sequentially on the rocket adapter (10), the plurality of satellites (20) being configured to be locked together by a release device; wherein the release device includes: The locking part is configured to include a first locking member (31) and a second locking member (32) that are movably connected; the first locking member (31) and the second locking member (32) are configured to be held in a tensioned state by a release; the first locking member (31) is configured to be hinged to the rocket adapter (10), and the top end of the second locking member (32) is configured to press against the end face of the top satellite (20); when the release releases the second locking member (32), the second locking member (32) is configured to move toward the top satellite (20) under the action of a first elastic member (41) to unlock from the top satellite (20); The ejector (50) is configured to be movably connected to the rocket adapter (10) and is configured to be pre-pressed onto the first locking member (31) by a second elastic member (42); the ejector (50) is configured to push the first locking member (31) outward under the action of the second elastic member (42) after the second locking member (32) unlocks the top satellite (20); The first locking member (31) and the second locking member (32) are configured to engage in a guiding mechanism, and the second locking member (32) is configured to move along its axial direction under the guidance of the guiding mechanism. The guiding mechanism includes a first guide seat (61) disposed on the first locking member (31) and a second guide seat (62) disposed on the second locking member (32); a guide post (63) is disposed on one of the first guide seat (61) and the second guide seat (62), and a guide hole is disposed on the other for guiding and cooperating with the guide post (63); The first elastic element (41) is configured to be sleeved on the guide post (63), one end of the first elastic element (41) is configured to abut against the first guide seat (61), and the other end is configured to abut against the second guide seat (62).

2. The multi-satellite stacking system according to claim 1, characterized in that, Two guide posts (63) and two guide holes are provided, and the two guide posts (63) and guide holes are constructed to be symmetrical with respect to the axes of the first locking member (31) and the second locking member (32).

3. The multi-satellite stacking system according to claim 1, characterized in that, The release device is an explosive bolt (64), and the two ends of the explosive bolt (64) are configured to connect to the first locking member (31) and the second locking member (32) respectively.

4. The multi-satellite stacking system according to claim 3, characterized in that, The first locking member (31) and the second locking member (32) are constructed in the form of rods, and the explosion bolt (64), the first locking member (31), and the second locking member (32) are constructed to be coaxially arranged.

5. The multi-satellite stacking system according to claim 1, characterized in that, The top satellite (20) is provided with a locking seat (71), and the top end of the second locking member (32) is provided with a pressing part (72), which is configured to press against the top end face of the locking seat (71).

6. The multi-satellite stacking system according to claim 5, characterized in that, The second locking member (32) has a threaded section (321) at its top, and the pressing part (72) is configured to be sleeved on the threaded section (321); a first locking nut (73) is provided on the threaded section (321) at a position outside the pressing part (72), and the first locking nut (73) is configured to press the pressing part (72) against the end face of the locking seat (71) by rotation.

7. The multi-satellite stacking system according to claim 6, characterized in that, A second locking nut (74) is provided on the threaded section (321) at the bottom of the clamping part (72), and the second locking nut (74) is configured to abut against the clamping part (72) by rotation.

8. The multi-satellite stacking system according to claim 5, characterized in that, Multiple release devices are provided, and the multiple release devices are configured to be distributed in the circumferential direction of the satellite (20).

9. The multi-satellite stacking system according to claim 8, characterized in that, The satellite (20) is cross-shaped in general. The four side walls of the satellite (20) are provided with protrusions (21) extending in their respective directions. The connection position of two adjacent protrusions (21) is constructed to have a chamfered structure (22). The locking seat (71) is constructed to be set on the chamfered structure (22) of the top satellite (20).

10. The multi-satellite stacking system according to claim 1, characterized in that, The rocket adapter (10) is provided with a mounting base (80), and the first locking member (31) is configured to be hinged to the mounting base (80) via a rotating part (311); the rotating part (311) is provided with a locking hole; the mounting base (80) is provided with a locking pin (81), and the locking pin (81) is configured to be pre-pressed on the end face of the rotating part (311) by a third elastic member; the rotating part (311) is configured to be rotated relative to the mounting base (80) to a predetermined angle, and the locking pin (81) is configured to extend into the locking hole under the action of the third elastic member to lock the rotating part (311).

11. The multi-satellite stacking system according to claim 1, characterized in that, The upper and lower satellites are configured to have a positioning unit; the positioning unit is a first cone (91) and a second cone (92) respectively located at the bottom of the upper satellite and the top of the lower satellite.

12. The multi-satellite stacking system according to claim 11, characterized in that, The first truncated cone (91) and the second truncated cone (92) have a predetermined angle between their conical surfaces.

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